US 11,939,880 B1
Airfoil assembly with flow surface
Paul Hadley Vitt, Liberty Township, OH (US); Matthew Brian Surprenant, Stoneham, MA (US); Brian David Keith, Cincinnati, OH (US); Prem Venugopal, Clifton Park, NY (US); and Thomas William Vandeputte, Scotia, NY (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Nov. 3, 2022, as Appl. No. 17/980,134.
Int. Cl. F01D 5/02 (2006.01); F01D 5/14 (2006.01)
CPC F01D 5/02 (2013.01) [F01D 5/14 (2013.01); F05D 2220/30 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A turbine engine stage for at least one of a compressor or a turbine, the turbine engine stage comprising:
a plurality of airfoils extending between an inner band and an outer band, each airfoil in the plurality of airfoils having an outer wall defining a pressure side and a suction side, with the outer wall extending between a leading edge and a trailing edge; and
an intervening flow passage defined between a first airfoil and a second airfoil in the plurality of airfoils;
wherein at least one of the inner band or the outer band includes a platform extending along an axial direction between a forward edge and an aft edge, with the platform having a contoured flow surface comprising:
a trough extending along at least a portion of the pressure side of the first airfoil and having a local minimum proximate the leading edge of the first airfoil; and
a bulge positioned in the intervening flow passage and having a local maximum spaced from each of the first airfoil and the second airfoil;
wherein each of the bulge and the trough are positioned aft of the forward edge of the platform.